LIQUID-PROPELLANT ROCKET ENGINE AND METHOD OF COOLING ITS CHAMBER HIGH-HEAT AREAS Russian patent published in 2013 - IPC F02K9/64 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises, at least, one chamber with regenerative cooling, device to feed working medium to turbo pump unit turbine, supply and control units. Said chamber comprises mixing head, shaped shell consisting of shaped inner and outer rings welded together by ribs made on outer shell. Shaped shell has, at least, one belt of curtain composed of annular shaped groove in inner shell communicated via channels with cooler, e.g. kerosene, feed chamber. Axes of said channels are arranged tangentially to curtain annular chamber. Chamber is provided with, at least, one curtain belt wherein axes of larger part of, preferably, all tangential channels are located outside the plane perpendicular to chamber axis to cross it. In compliance with another version, axes of tangential channels cross said plane at 4-10°, preferably 6°, while channel length-to-diameter makes 3 to 8. Invention covers also method of cooling high-heat areas of combustion chamber.

EFFECT: higher reliability at minimum thrust pulse minimum losses for cooling.

7 cl, 5 dwg